EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 100,000 Max Cl/Cd: 46.2 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e748-il-100000-n5.txt Download as CSV file: xf-e748-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 748 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3647 0.13346 0.12791 -0.0497 1.0000 0.0347
-14.250 -0.5335 0.09170 0.08553 -0.0707 1.0000 0.0329
-14.000 -0.5554 0.08509 0.07875 -0.0738 1.0000 0.0329
-13.750 -0.5676 0.08050 0.07406 -0.0755 1.0000 0.0333
-13.500 -0.5777 0.07642 0.06988 -0.0768 1.0000 0.0335
-13.250 -0.5859 0.07286 0.06622 -0.0776 1.0000 0.0339
-13.000 -0.5929 0.06965 0.06292 -0.0781 1.0000 0.0343
-12.750 -0.5998 0.06669 0.05987 -0.0783 1.0000 0.0349
-12.500 -0.6057 0.06400 0.05708 -0.0782 1.0000 0.0354
-12.250 -0.6106 0.06156 0.05454 -0.0777 1.0000 0.0359
-12.000 -0.6130 0.05950 0.05240 -0.0768 1.0000 0.0364
-11.750 -0.6150 0.05766 0.05049 -0.0756 1.0000 0.0370
-11.500 -0.6139 0.05638 0.04927 -0.0740 1.0000 0.0375
-11.250 -0.6152 0.05508 0.04800 -0.0722 1.0000 0.0380
-11.000 -0.6187 0.05381 0.04676 -0.0702 1.0000 0.0386
-10.750 -0.5940 0.05214 0.04506 -0.0728 0.9951 0.0398
-10.500 -0.5663 0.05058 0.04340 -0.0755 0.9889 0.0416
-10.250 -0.5379 0.04915 0.04195 -0.0784 0.9826 0.0433
-10.000 -0.5162 0.04739 0.04020 -0.0809 0.9733 0.0458
-9.750 -0.4950 0.04583 0.03859 -0.0828 0.9630 0.0490
-9.500 -0.4794 0.04406 0.03687 -0.0844 0.9501 0.0517
-9.250 -0.4646 0.04250 0.03526 -0.0853 0.9357 0.0558
-9.000 -0.4558 0.04056 0.03339 -0.0862 0.9197 0.0595
-8.750 -0.4460 0.03872 0.03153 -0.0869 0.9043 0.0646
-8.500 -0.4334 0.03638 0.02920 -0.0889 0.8897 0.0714
-8.250 -0.4152 0.03381 0.02664 -0.0923 0.8761 0.0813
-8.000 -0.3893 0.03092 0.02374 -0.0978 0.8648 0.0961
-7.750 -0.3632 0.02792 0.02074 -0.1039 0.8502 0.1154
-7.500 -0.3311 0.02528 0.01814 -0.1101 0.8369 0.1450
-7.250 -0.2930 0.02266 0.01574 -0.1171 0.8250 0.1998
-7.000 -0.2541 0.02211 0.01571 -0.1204 0.8124 0.2719
-6.750 -0.2167 0.02254 0.01614 -0.1216 0.7983 0.3115
-6.500 -0.1782 0.02263 0.01596 -0.1237 0.7844 0.3360
-6.250 -0.1397 0.02267 0.01569 -0.1259 0.7709 0.3543
-6.000 -0.1050 0.02321 0.01606 -0.1264 0.7570 0.3653
-5.750 -0.0731 0.02331 0.01592 -0.1273 0.7428 0.3770
-5.500 -0.0420 0.02381 0.01628 -0.1272 0.7297 0.3854
-5.250 -0.0092 0.02389 0.01611 -0.1282 0.7178 0.3946
-5.000 0.0181 0.02436 0.01650 -0.1272 0.7049 0.4005
-4.750 0.0488 0.02404 0.01591 -0.1287 0.6932 0.4105
-4.500 0.0767 0.02449 0.01628 -0.1277 0.6826 0.4145
-4.250 0.1033 0.02459 0.01628 -0.1272 0.6714 0.4199
-4.000 0.1357 0.02401 0.01535 -0.1294 0.6620 0.4283
-3.750 0.1607 0.02411 0.01541 -0.1285 0.6515 0.4309
-3.500 0.1887 0.02413 0.01530 -0.1283 0.6428 0.4342
-3.250 0.2155 0.02399 0.01506 -0.1284 0.6332 0.4382
-3.000 0.2466 0.02365 0.01446 -0.1297 0.6255 0.4432
-2.750 0.2752 0.02329 0.01394 -0.1306 0.6163 0.4473
-2.500 0.3028 0.02324 0.01378 -0.1305 0.6089 0.4495
-2.250 0.3294 0.02316 0.01364 -0.1304 0.6008 0.4518
-2.000 0.3574 0.02306 0.01343 -0.1306 0.5935 0.4546
-1.750 0.3866 0.02294 0.01316 -0.1312 0.5870 0.4577
-1.500 0.4150 0.02276 0.01287 -0.1318 0.5793 0.4608
-1.250 0.4459 0.02255 0.01245 -0.1329 0.5730 0.4639
-1.000 0.4739 0.02248 0.01230 -0.1332 0.5665 0.4663
-0.750 0.5005 0.02247 0.01226 -0.1331 0.5600 0.4682
-0.500 0.5289 0.02246 0.01216 -0.1333 0.5545 0.4702
-0.250 0.5566 0.02245 0.01209 -0.1335 0.5485 0.4722
0.000 0.5840 0.02244 0.01203 -0.1336 0.5422 0.4744
0.250 0.6131 0.02244 0.01192 -0.1341 0.5370 0.4770
0.500 0.6421 0.02247 0.01185 -0.1346 0.5320 0.4801
0.750 0.6702 0.02251 0.01182 -0.1351 0.5262 0.4830
1.000 0.6979 0.02255 0.01182 -0.1352 0.5210 0.4849
1.250 0.7266 0.02261 0.01181 -0.1354 0.5167 0.4866
1.500 0.7519 0.02273 0.01198 -0.1352 0.5111 0.4885
1.750 0.7785 0.02285 0.01210 -0.1351 0.5060 0.4906
2.000 0.8066 0.02296 0.01217 -0.1353 0.5017 0.4932
2.250 0.8356 0.02310 0.01221 -0.1357 0.4978 0.4962
2.500 0.8607 0.02328 0.01245 -0.1355 0.4924 0.4993
2.750 0.8878 0.02345 0.01257 -0.1357 0.4875 0.5023
3.000 0.9148 0.02358 0.01271 -0.1356 0.4834 0.5043
3.250 0.9428 0.02376 0.01287 -0.1357 0.4800 0.5066
3.500 0.9657 0.02403 0.01324 -0.1351 0.4751 0.5090
3.750 0.9907 0.02425 0.01351 -0.1348 0.4705 0.5118
4.000 1.0177 0.02445 0.01370 -0.1348 0.4664 0.5150
4.250 1.0469 0.02466 0.01382 -0.1353 0.4630 0.5187
4.500 1.0693 0.02500 0.01428 -0.1346 0.4586 0.5219
4.750 1.0921 0.02531 0.01472 -0.1339 0.4542 0.5250
5.000 1.1172 0.02557 0.01502 -0.1336 0.4501 0.5286
5.250 1.1448 0.02580 0.01522 -0.1337 0.4467 0.5325
5.500 1.1691 0.02616 0.01563 -0.1334 0.4429 0.5364
5.750 1.1894 0.02659 0.01620 -0.1324 0.4385 0.5401
6.000 1.2120 0.02694 0.01664 -0.1318 0.4343 0.5437
6.250 1.2376 0.02721 0.01696 -0.1315 0.4307 0.5481
6.500 1.2663 0.02747 0.01718 -0.1319 0.4276 0.5537
6.750 1.2820 0.02807 0.01796 -0.1302 0.4232 0.5588
7.000 1.3004 0.02855 0.01860 -0.1289 0.4189 0.5639
7.250 1.3230 0.02892 0.01903 -0.1283 0.4150 0.5703
7.500 1.3494 0.02921 0.01933 -0.1282 0.4118 0.5776
7.750 1.3694 0.02969 0.01994 -0.1272 0.4082 0.5842
8.000 1.3810 0.03040 0.02085 -0.1251 0.4037 0.5915
8.250 1.3983 0.03092 0.02149 -0.1237 0.3996 0.5994
8.500 1.4210 0.03127 0.02192 -0.1231 0.3961 0.6097
8.750 1.4491 0.03151 0.02219 -0.1233 0.3931 0.6220
9.000 1.4496 0.03246 0.02340 -0.1195 0.3887 0.6337
9.250 1.4562 0.03326 0.02440 -0.1167 0.3844 0.6487
9.500 1.4723 0.03375 0.02504 -0.1152 0.3806 0.6689
9.750 1.4963 0.03397 0.02537 -0.1147 0.3774 0.6977
10.000 1.5021 0.03479 0.02642 -0.1118 0.3736 0.7327
10.250 1.4929 0.03605 0.02802 -0.1071 0.3690 0.7835
10.500 1.4892 0.03665 0.02887 -0.1028 0.3652 1.0000
10.750 1.5116 0.03709 0.02930 -0.1024 0.3616 1.0000
11.000 1.5282 0.03783 0.03005 -0.1015 0.3580 1.0000
11.250 1.5045 0.04064 0.03310 -0.0970 0.3526 1.0000
11.500 1.5067 0.04224 0.03478 -0.0952 0.3481 1.0000
11.750 1.5315 0.04247 0.03499 -0.0950 0.3445 1.0000
12.000 1.5241 0.04484 0.03750 -0.0928 0.3400 1.0000
12.250 1.4832 0.05011 0.04300 -0.0898 0.3336 1.0000
12.500 1.4997 0.05093 0.04385 -0.0892 0.3296 1.0000
12.750 1.5410 0.04966 0.04251 -0.0895 0.3266 1.0000
13.000 1.4138 0.06497 0.05825 -0.0876 0.3148 1.0000
13.250 1.4538 0.06313 0.05640 -0.0870 0.3124 1.0000
13.500 1.5052 0.06015 0.05336 -0.0865 0.3103 1.0000
13.750 1.3428 0.08373 0.07731 -0.0899 0.2919 1.0000
14.000 1.4145 0.07686 0.07040 -0.0878 0.2936 1.0000
14.500 1.3794 0.08826 0.08199 -0.0899 0.2786 1.0000
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